EP1966107A2 - Gelötete verbindung zwischen einem metallteil auf titanbasis und einem keramischen teil auf basis von siliciumcarbid (sic) und/oder kohlenstoff - Google Patents
Gelötete verbindung zwischen einem metallteil auf titanbasis und einem keramischen teil auf basis von siliciumcarbid (sic) und/oder kohlenstoffInfo
- Publication number
- EP1966107A2 EP1966107A2 EP06842128A EP06842128A EP1966107A2 EP 1966107 A2 EP1966107 A2 EP 1966107A2 EP 06842128 A EP06842128 A EP 06842128A EP 06842128 A EP06842128 A EP 06842128A EP 1966107 A2 EP1966107 A2 EP 1966107A2
- Authority
- EP
- European Patent Office
- Prior art keywords
- assembly according
- ceramic material
- metal part
- brazing
- piece
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
Links
- 229910052751 metal Inorganic materials 0.000 title claims abstract description 46
- 239000002184 metal Substances 0.000 title claims abstract description 45
- HBMJWWWQQXIZIP-UHFFFAOYSA-N silicon carbide Chemical compound [Si+]#[C-] HBMJWWWQQXIZIP-UHFFFAOYSA-N 0.000 title claims abstract description 29
- 239000000919 ceramic Substances 0.000 title claims abstract description 26
- 239000010936 titanium Substances 0.000 title claims abstract description 26
- RTAQQCXQSZGOHL-UHFFFAOYSA-N Titanium Chemical compound [Ti] RTAQQCXQSZGOHL-UHFFFAOYSA-N 0.000 title claims abstract description 21
- 229910052719 titanium Inorganic materials 0.000 title claims abstract description 21
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 title claims abstract description 16
- 229910052799 carbon Inorganic materials 0.000 title claims abstract description 16
- 229910010271 silicon carbide Inorganic materials 0.000 claims abstract description 29
- 238000005219 brazing Methods 0.000 claims abstract description 27
- 125000006850 spacer group Chemical group 0.000 claims abstract description 16
- WFKWXMTUELFFGS-UHFFFAOYSA-N tungsten Chemical compound [W] WFKWXMTUELFFGS-UHFFFAOYSA-N 0.000 claims abstract description 7
- 229910052721 tungsten Inorganic materials 0.000 claims abstract description 7
- 239000010937 tungsten Substances 0.000 claims abstract description 7
- 229910010293 ceramic material Inorganic materials 0.000 claims description 49
- 239000000463 material Substances 0.000 claims description 20
- 239000011159 matrix material Substances 0.000 claims description 15
- 239000011229 interlayer Substances 0.000 claims description 14
- 229910000679 solder Inorganic materials 0.000 claims description 14
- PMHQVHHXPFUNSP-UHFFFAOYSA-M copper(1+);methylsulfanylmethane;bromide Chemical compound Br[Cu].CSC PMHQVHHXPFUNSP-UHFFFAOYSA-M 0.000 claims description 12
- 239000010410 layer Substances 0.000 claims description 9
- 239000011572 manganese Substances 0.000 claims description 9
- 238000002485 combustion reaction Methods 0.000 claims description 8
- BQCADISMDOOEFD-UHFFFAOYSA-N Silver Chemical compound [Ag] BQCADISMDOOEFD-UHFFFAOYSA-N 0.000 claims description 7
- 229910052709 silver Inorganic materials 0.000 claims description 7
- 239000004332 silver Substances 0.000 claims description 7
- 229910017945 Cu—Ti Inorganic materials 0.000 claims description 6
- 229910052782 aluminium Inorganic materials 0.000 claims description 6
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 claims description 6
- 229920000049 Carbon (fiber) Polymers 0.000 claims description 5
- 229910045601 alloy Inorganic materials 0.000 claims description 5
- 239000000956 alloy Substances 0.000 claims description 5
- 239000004917 carbon fiber Substances 0.000 claims description 5
- 229910052720 vanadium Inorganic materials 0.000 claims description 5
- LEONUFNNVUYDNQ-UHFFFAOYSA-N vanadium atom Chemical compound [V] LEONUFNNVUYDNQ-UHFFFAOYSA-N 0.000 claims description 5
- PWHULOQIROXLJO-UHFFFAOYSA-N Manganese Chemical compound [Mn] PWHULOQIROXLJO-UHFFFAOYSA-N 0.000 claims description 4
- 229910052748 manganese Inorganic materials 0.000 claims description 4
- 239000007787 solid Substances 0.000 claims description 4
- 238000005476 soldering Methods 0.000 claims description 3
- 229910017083 AlN Inorganic materials 0.000 abstract 2
- PIGFYZPCRLYGLF-UHFFFAOYSA-N Aluminum nitride Chemical compound [Al]#N PIGFYZPCRLYGLF-UHFFFAOYSA-N 0.000 abstract 2
- 239000011153 ceramic matrix composite Substances 0.000 description 8
- 230000000712 assembly Effects 0.000 description 6
- 238000000429 assembly Methods 0.000 description 6
- 239000000126 substance Substances 0.000 description 6
- 239000000203 mixture Substances 0.000 description 5
- 230000002787 reinforcement Effects 0.000 description 5
- 230000015572 biosynthetic process Effects 0.000 description 4
- 150000001875 compounds Chemical class 0.000 description 4
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 description 4
- 238000000034 method Methods 0.000 description 4
- 239000002131 composite material Substances 0.000 description 3
- 238000001816 cooling Methods 0.000 description 3
- 239000000835 fiber Substances 0.000 description 3
- 238000004519 manufacturing process Methods 0.000 description 3
- 150000002739 metals Chemical class 0.000 description 3
- 230000000930 thermomechanical effect Effects 0.000 description 3
- 230000004888 barrier function Effects 0.000 description 2
- 230000008901 benefit Effects 0.000 description 2
- 238000002844 melting Methods 0.000 description 2
- 230000008018 melting Effects 0.000 description 2
- 229910001092 metal group alloy Inorganic materials 0.000 description 2
- 230000005012 migration Effects 0.000 description 2
- 238000013508 migration Methods 0.000 description 2
- 230000008569 process Effects 0.000 description 2
- 229910017944 Ag—Cu Inorganic materials 0.000 description 1
- XUIMIQQOPSSXEZ-UHFFFAOYSA-N Silicon Chemical compound [Si] XUIMIQQOPSSXEZ-UHFFFAOYSA-N 0.000 description 1
- 229910001069 Ti alloy Inorganic materials 0.000 description 1
- CFOAUMXQOCBWNJ-UHFFFAOYSA-N [B].[Si] Chemical compound [B].[Si] CFOAUMXQOCBWNJ-UHFFFAOYSA-N 0.000 description 1
- 230000002238 attenuated effect Effects 0.000 description 1
- 230000006399 behavior Effects 0.000 description 1
- 238000005452 bending Methods 0.000 description 1
- 150000001721 carbon Chemical class 0.000 description 1
- 239000012700 ceramic precursor Substances 0.000 description 1
- 229910052729 chemical element Inorganic materials 0.000 description 1
- 238000006243 chemical reaction Methods 0.000 description 1
- 230000006835 compression Effects 0.000 description 1
- 238000007906 compression Methods 0.000 description 1
- 239000000470 constituent Substances 0.000 description 1
- 230000001627 detrimental effect Effects 0.000 description 1
- 230000002349 favourable effect Effects 0.000 description 1
- 239000008187 granular material Substances 0.000 description 1
- 229910000765 intermetallic Inorganic materials 0.000 description 1
- 239000000843 powder Substances 0.000 description 1
- 230000000750 progressive effect Effects 0.000 description 1
- 238000000197 pyrolysis Methods 0.000 description 1
- 230000000717 retained effect Effects 0.000 description 1
- 229910052710 silicon Inorganic materials 0.000 description 1
- 239000010703 silicon Substances 0.000 description 1
- 238000005245 sintering Methods 0.000 description 1
- 238000007711 solidification Methods 0.000 description 1
- 230000008023 solidification Effects 0.000 description 1
- 238000009736 wetting Methods 0.000 description 1
Classifications
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- C—CHEMISTRY; METALLURGY
- C04—CEMENTS; CONCRETE; ARTIFICIAL STONE; CERAMICS; REFRACTORIES
- C04B—LIME, MAGNESIA; SLAG; CEMENTS; COMPOSITIONS THEREOF, e.g. MORTARS, CONCRETE OR LIKE BUILDING MATERIALS; ARTIFICIAL STONE; CERAMICS; REFRACTORIES; TREATMENT OF NATURAL STONE
- C04B37/00—Joining burned ceramic articles with other burned ceramic articles or other articles by heating
- C04B37/02—Joining burned ceramic articles with other burned ceramic articles or other articles by heating with metallic articles
- C04B37/023—Joining burned ceramic articles with other burned ceramic articles or other articles by heating with metallic articles characterised by the interlayer used
- C04B37/025—Joining burned ceramic articles with other burned ceramic articles or other articles by heating with metallic articles characterised by the interlayer used consisting of glass or ceramic material
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- C—CHEMISTRY; METALLURGY
- C04—CEMENTS; CONCRETE; ARTIFICIAL STONE; CERAMICS; REFRACTORIES
- C04B—LIME, MAGNESIA; SLAG; CEMENTS; COMPOSITIONS THEREOF, e.g. MORTARS, CONCRETE OR LIKE BUILDING MATERIALS; ARTIFICIAL STONE; CERAMICS; REFRACTORIES; TREATMENT OF NATURAL STONE
- C04B37/00—Joining burned ceramic articles with other burned ceramic articles or other articles by heating
- C04B37/02—Joining burned ceramic articles with other burned ceramic articles or other articles by heating with metallic articles
- C04B37/023—Joining burned ceramic articles with other burned ceramic articles or other articles by heating with metallic articles characterised by the interlayer used
- C04B37/026—Joining burned ceramic articles with other burned ceramic articles or other articles by heating with metallic articles characterised by the interlayer used consisting of metals or metal salts
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/28—Selecting particular materials; Particular measures relating thereto; Measures against erosion or corrosion
- F01D5/284—Selection of ceramic materials
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D9/00—Stators
- F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
- F01D9/023—Transition ducts between combustor cans and first stage of the turbine in gas-turbine engines; their cooling or sealings
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D9/00—Stators
- F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
- F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
- F01D9/041—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector using blades
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K3/00—Plants including a gas turbine driving a compressor or a ducted fan
- F02K3/08—Plants including a gas turbine driving a compressor or a ducted fan with supplementary heating of the working fluid; Control thereof
- F02K3/10—Plants including a gas turbine driving a compressor or a ducted fan with supplementary heating of the working fluid; Control thereof by after-burners
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/007—Continuous combustion chambers using liquid or gaseous fuel constructed mainly of ceramic components
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B2311/00—Metals, their alloys or their compounds
- B32B2311/18—Titanium
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- C—CHEMISTRY; METALLURGY
- C04—CEMENTS; CONCRETE; ARTIFICIAL STONE; CERAMICS; REFRACTORIES
- C04B—LIME, MAGNESIA; SLAG; CEMENTS; COMPOSITIONS THEREOF, e.g. MORTARS, CONCRETE OR LIKE BUILDING MATERIALS; ARTIFICIAL STONE; CERAMICS; REFRACTORIES; TREATMENT OF NATURAL STONE
- C04B2235/00—Aspects relating to ceramic starting mixtures or sintered ceramic products
- C04B2235/02—Composition of constituents of the starting material or of secondary phases of the final product
- C04B2235/50—Constituents or additives of the starting mixture chosen for their shape or used because of their shape or their physical appearance
- C04B2235/52—Constituents or additives characterised by their shapes
- C04B2235/5208—Fibers
- C04B2235/5216—Inorganic
- C04B2235/524—Non-oxidic, e.g. borides, carbides, silicides or nitrides
- C04B2235/5244—Silicon carbide
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- C—CHEMISTRY; METALLURGY
- C04—CEMENTS; CONCRETE; ARTIFICIAL STONE; CERAMICS; REFRACTORIES
- C04B—LIME, MAGNESIA; SLAG; CEMENTS; COMPOSITIONS THEREOF, e.g. MORTARS, CONCRETE OR LIKE BUILDING MATERIALS; ARTIFICIAL STONE; CERAMICS; REFRACTORIES; TREATMENT OF NATURAL STONE
- C04B2235/00—Aspects relating to ceramic starting mixtures or sintered ceramic products
- C04B2235/02—Composition of constituents of the starting material or of secondary phases of the final product
- C04B2235/50—Constituents or additives of the starting mixture chosen for their shape or used because of their shape or their physical appearance
- C04B2235/52—Constituents or additives characterised by their shapes
- C04B2235/5208—Fibers
- C04B2235/5216—Inorganic
- C04B2235/524—Non-oxidic, e.g. borides, carbides, silicides or nitrides
- C04B2235/5248—Carbon, e.g. graphite
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- C—CHEMISTRY; METALLURGY
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- C04B2237/00—Aspects relating to ceramic laminates or to joining of ceramic articles with other articles by heating
- C04B2237/02—Aspects relating to interlayers, e.g. used to join ceramic articles with other articles by heating
- C04B2237/12—Metallic interlayers
- C04B2237/125—Metallic interlayers based on noble metals, e.g. silver
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- C—CHEMISTRY; METALLURGY
- C04—CEMENTS; CONCRETE; ARTIFICIAL STONE; CERAMICS; REFRACTORIES
- C04B—LIME, MAGNESIA; SLAG; CEMENTS; COMPOSITIONS THEREOF, e.g. MORTARS, CONCRETE OR LIKE BUILDING MATERIALS; ARTIFICIAL STONE; CERAMICS; REFRACTORIES; TREATMENT OF NATURAL STONE
- C04B2237/00—Aspects relating to ceramic laminates or to joining of ceramic articles with other articles by heating
- C04B2237/30—Composition of layers of ceramic laminates or of ceramic or metallic articles to be joined by heating, e.g. Si substrates
- C04B2237/32—Ceramic
- C04B2237/36—Non-oxidic
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- C—CHEMISTRY; METALLURGY
- C04—CEMENTS; CONCRETE; ARTIFICIAL STONE; CERAMICS; REFRACTORIES
- C04B—LIME, MAGNESIA; SLAG; CEMENTS; COMPOSITIONS THEREOF, e.g. MORTARS, CONCRETE OR LIKE BUILDING MATERIALS; ARTIFICIAL STONE; CERAMICS; REFRACTORIES; TREATMENT OF NATURAL STONE
- C04B2237/00—Aspects relating to ceramic laminates or to joining of ceramic articles with other articles by heating
- C04B2237/30—Composition of layers of ceramic laminates or of ceramic or metallic articles to be joined by heating, e.g. Si substrates
- C04B2237/32—Ceramic
- C04B2237/36—Non-oxidic
- C04B2237/365—Silicon carbide
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- C—CHEMISTRY; METALLURGY
- C04—CEMENTS; CONCRETE; ARTIFICIAL STONE; CERAMICS; REFRACTORIES
- C04B—LIME, MAGNESIA; SLAG; CEMENTS; COMPOSITIONS THEREOF, e.g. MORTARS, CONCRETE OR LIKE BUILDING MATERIALS; ARTIFICIAL STONE; CERAMICS; REFRACTORIES; TREATMENT OF NATURAL STONE
- C04B2237/00—Aspects relating to ceramic laminates or to joining of ceramic articles with other articles by heating
- C04B2237/30—Composition of layers of ceramic laminates or of ceramic or metallic articles to be joined by heating, e.g. Si substrates
- C04B2237/32—Ceramic
- C04B2237/38—Fiber or whisker reinforced
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- C—CHEMISTRY; METALLURGY
- C04—CEMENTS; CONCRETE; ARTIFICIAL STONE; CERAMICS; REFRACTORIES
- C04B—LIME, MAGNESIA; SLAG; CEMENTS; COMPOSITIONS THEREOF, e.g. MORTARS, CONCRETE OR LIKE BUILDING MATERIALS; ARTIFICIAL STONE; CERAMICS; REFRACTORIES; TREATMENT OF NATURAL STONE
- C04B2237/00—Aspects relating to ceramic laminates or to joining of ceramic articles with other articles by heating
- C04B2237/30—Composition of layers of ceramic laminates or of ceramic or metallic articles to be joined by heating, e.g. Si substrates
- C04B2237/32—Ceramic
- C04B2237/38—Fiber or whisker reinforced
- C04B2237/385—Carbon or carbon composite
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- C—CHEMISTRY; METALLURGY
- C04—CEMENTS; CONCRETE; ARTIFICIAL STONE; CERAMICS; REFRACTORIES
- C04B—LIME, MAGNESIA; SLAG; CEMENTS; COMPOSITIONS THEREOF, e.g. MORTARS, CONCRETE OR LIKE BUILDING MATERIALS; ARTIFICIAL STONE; CERAMICS; REFRACTORIES; TREATMENT OF NATURAL STONE
- C04B2237/00—Aspects relating to ceramic laminates or to joining of ceramic articles with other articles by heating
- C04B2237/30—Composition of layers of ceramic laminates or of ceramic or metallic articles to be joined by heating, e.g. Si substrates
- C04B2237/40—Metallic
- C04B2237/403—Refractory metals
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2230/00—Manufacture
- F05D2230/20—Manufacture essentially without removing material
- F05D2230/23—Manufacture essentially without removing material by permanently joining parts together
- F05D2230/232—Manufacture essentially without removing material by permanently joining parts together by welding
- F05D2230/237—Brazing
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2300/00—Materials; Properties thereof
- F05D2300/10—Metals, alloys or intermetallic compounds
- F05D2300/13—Refractory metals, i.e. Ti, V, Cr, Zr, Nb, Mo, Hf, Ta, W
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2300/00—Materials; Properties thereof
- F05D2300/10—Metals, alloys or intermetallic compounds
- F05D2300/13—Refractory metals, i.e. Ti, V, Cr, Zr, Nb, Mo, Hf, Ta, W
- F05D2300/133—Titanium
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2300/00—Materials; Properties thereof
- F05D2300/20—Oxide or non-oxide ceramics
- F05D2300/21—Oxide ceramics
- F05D2300/211—Silica
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2300/00—Materials; Properties thereof
- F05D2300/20—Oxide or non-oxide ceramics
- F05D2300/22—Non-oxide ceramics
- F05D2300/224—Carbon, e.g. graphite
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2300/00—Materials; Properties thereof
- F05D2300/20—Oxide or non-oxide ceramics
- F05D2300/22—Non-oxide ceramics
- F05D2300/226—Carbides
- F05D2300/2261—Carbides of silicon
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2300/00—Materials; Properties thereof
- F05D2300/60—Properties or characteristics given to material by treatment or manufacturing
- F05D2300/603—Composites; e.g. fibre-reinforced
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23M—CASINGS, LININGS, WALLS OR DOORS SPECIALLY ADAPTED FOR COMBUSTION CHAMBERS, e.g. FIREBRIDGES; DEVICES FOR DEFLECTING AIR, FLAMES OR COMBUSTION PRODUCTS IN COMBUSTION CHAMBERS; SAFETY ARRANGEMENTS SPECIALLY ADAPTED FOR COMBUSTION APPARATUS; DETAILS OF COMBUSTION CHAMBERS, NOT OTHERWISE PROVIDED FOR
- F23M2900/00—Special features of, or arrangements for combustion chambers
- F23M2900/05004—Special materials for walls or lining
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
- Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
- Y10T428/00—Stock material or miscellaneous articles
- Y10T428/12—All metal or with adjacent metals
- Y10T428/12493—Composite; i.e., plural, adjacent, spatially distinct metal components [e.g., layers, joint, etc.]
- Y10T428/12535—Composite; i.e., plural, adjacent, spatially distinct metal components [e.g., layers, joint, etc.] with additional, spatially distinct nonmetal component
- Y10T428/12576—Boride, carbide or nitride component
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
- Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
- Y10T428/00—Stock material or miscellaneous articles
- Y10T428/12—All metal or with adjacent metals
- Y10T428/12493—Composite; i.e., plural, adjacent, spatially distinct metal components [e.g., layers, joint, etc.]
- Y10T428/12736—Al-base component
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
- Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
- Y10T428/00—Stock material or miscellaneous articles
- Y10T428/31504—Composite [nonstructural laminate]
- Y10T428/31678—Of metal
Definitions
- the present invention relates to the field of assembly by brazing of a metallic piece of titanium and a piece of ceramic material based on silicon carbide (SiC) and / or carbon.
- ceramic materials are characterized by their mechanical properties which make them suitable for constituting structural elements and by their capacity to maintain these mechanical properties at high temperature. These materials are used in particular for the manufacture of parts undergoing high thermomechanical stresses in aeronautical applications (engine parts or fairing elements).
- connection between ceramic materials and metals is traditionally done by a mechanical connection of the riveting or bolting type, connection sometimes unsuitable for reasons of space or difficulties of implementation.
- the known brazing techniques used for homogeneous ceramic / ceramic bonds can hardly be used for heterogeneous brazing of ceramic material on metal because of the very different thermomechanical and chemical behaviors of ceramic materials and metals.
- the greater relative shrinkage of the metal part generates high stresses in the two parts and in particular a zone in compression, respectively in traction, in the zones adjacent to the solder joint of the ceramic part, respectively of the metal part.
- the invention proposes to solve the aforementioned problem by interposing, between the metal part and the part made of ceramic material, spacers with progressive coefficient of expansion thus constituting a stack of elements to be assembled thermally two by two by brazing.
- the main object of the present invention is therefore to solve these problems by proposing an assembly which makes it possible on the one hand to compensate for the difference in expansion between the metal part and the ceramic part and, on the other hand, to avoid or limit the formation of undesirable chemical compounds.
- the invention relates to an assembly between a metallic piece based on titanium and a piece made of ceramic material based on silicon carbide and / or carbon.
- This assembly comprises a stacked structure comprising the following elements assembled in pairs by brazing:
- first spacer able to deform to accommodate a differential expansion between the metal part and the part made of ceramic material
- a second rigid interlayer with a coefficient of expansion close to that of the part made of ceramic material, aluminum nitride or tungsten, and
- the invention therefore proposes to interpose between the ceramic and metallic parts two intermediate parts having distinct functions.
- the first intermediate piece makes it possible to compensate for the differences in expansion between the ceramic and metallic pieces, by deforming.
- the deformation of this part is obtained by producing the latter in a ductile metal.
- the piece of massive structure forms a layer of ductile material capable of elongating / shrinking between the ceramic and metallic pieces.
- the first spacer is preferably made of substantially pure titanium.
- the first spacer is constituted by a deformable structure ("compliant" in English).
- this structure comprises at least one intermediate connecting element assembled by brazing to the metal part and to the second intermediate, the intermediate connecting element consisting of a deformable sheet having brazed flat areas and deformable areas.
- this deformable structure is constituted by at least one part whose general shape is that of a ribbon folded in an accordion defining curved parts turned alternately towards the metal part and towards the second interlayer, the curved parts being separated by ridges, the assembly by brazing between the first interlayer on the one hand and the metal part or the second interlayer on the other hand being produced on a flat area of at least some of the ridges.
- the second intermediate piece has, first of all, a coefficient of expansion lower than that of the first metallic intermediate piece and preferably sufficiently close to that of the ceramic piece, in order to limit the differences in expansion between these pieces.
- the second intermediate piece acts as a chemical barrier by preventing the migration of metallic elements towards the ceramic piece, which makes it possible to avoid the formation of fragile chemical compounds, detrimental to the good performance of the assembly.
- this second intermediate piece can be chosen to be sufficiently elastic to allow the mechanical stresses exerted on the ceramic piece to be attenuated and sufficiently rigid to allow the mechanical stresses exerted on the ceramic piece to be distributed, which makes it possible to mechanically protect this piece which, by nature, is generally fragile.
- the metal part consists of an alloy based on titanium, aluminum and vanadium. This alloy is called "TA6V”.
- the coefficient of expansion of the TA6V alloy, at 500 ° C., is equal to 10.5.10 "6 K " 1 ⁇ 15%.
- the part made of ceramic material is formed from solid or monolithic silicon carbide.
- This material can in particular be obtained by sintering powder or granules of silicon carbide.
- the ceramic matrix can be single-phase, for example be made entirely of SiC.
- the matrix can alternatively be multi-phase, the matrix containing for example a sequence of alternating layers of different rigidities based on sintered silicon carbide and / or carbon pyrolysis and which can also comprise at least one self-healing phase such as a base layer boron silicon carbide Si-BC.
- the part made of ceramic material comprises a ceramic matrix reinforced with carbon or silicon carbide fibers, in particular with a layer of silicon carbide on the surface.
- this matrix can comprise at least one self-healing phase.
- a ceramic material hereinafter called "A410”
- A410 a process for obtaining this ceramic material are described in the French patent application published under the number 0 FR 2 732 338.
- the coefficient of expansion of the material "A410", at 500 ° C., is equal to 4.0.10 "6 K " 1 ⁇ 15%.
- the part made of ceramic material is a part made of thermostructural material comprising a fibrous carbon fiber reinforcement and a sequenced matrix with alternating layers of relatively flexible material capable of deflecting any cracks which reach them and of layers relatively rigid ceramic material.
- A500 Such a material, hereinafter called “A500”, can be obtained by a production process such as that described in patent application FR 2 742 433.
- the coefficient of expansion of the compound "A500”, at 500 ° C., is equal to 2.5.10 "6 K " 1 ⁇ 15%.
- the piece of ceramic material being very brittle, it is necessary that the second interlayer is able to absorb the forces and that its coefficient of expansion is close to the piece of ceramic material. Also, the inventors have advantageously retained, for this second interlayer, very rigid aluminum nitride (AIN) or tungsten (W) and with expansion coefficients very slightly greater than that of ceramic.
- AIN aluminum nitride
- W tungsten
- the coefficient of expansion of tungsten W and of aluminum nitride, at 500 ° C., are respectively equal to 5.0.10 "6 K " 1 ⁇ 15% and 5.2.10 "6 K " 1 ⁇ 15%.
- the solder used must be reactive, which means that it must react with at least one of the chemical elements of the facing materials.
- the solder used is a silver-based solder.
- this solder is of the Ag-Cu-Ti or Ag-Mn type.
- the weight percentage of silver is at least equal to 50% and the weight percentage of titanium is preferably chosen between 0.01% and 6%.
- This solder is indeed very reactive with aluminum, tungsten and silicon, including for small proportions of titanium.
- the Ag-Cu-Ti brazing selected by the invention comprises in weight percentages: 63 Ag, 35.25 Cu and 1.75 Ti.
- This brazing has the advantage of being commercially available under the name CuSiI-ABA (trade name).
- the weight percentage of manganese is preferably chosen between 1% and 25%, the proportion of manganese being explained by the fact that manganese has reactive properties with the abovementioned elements a little less than that of titanium.
- the invention also relates to a turbomachine nozzle comprising at least one assembly as mentioned above in which the metal part is a casing (or a lever) of this nozzle and the part made of ceramic material is a flap of this nozzle.
- the invention also relates to a turbomachine combustion chamber comprising at least one assembly as mentioned above in which the metal part is a casing (or a seal - that is to say a connecting element - or a part) of this chamber and the part made of ceramic material a component part of this chamber.
- the invention also relates to turbomachine post-combustion equipment comprising at least one assembly as mentioned above in which the metal part is an after-combustion casing (or a platform) and the part made of ceramic material is an arm flame catcher.
- the invention also relates to a turbomachine comprising at least one assembly as mentioned above.
- FIG. 1 shows an assembly according to a first embodiment of the invention
- FIG. 2 shows an assembly according to the invention in a second embodiment.
- Figure 1 shows an assembly according to the invention in a first embodiment. It consists mainly of four parts assembled two by two by brazing, namely:
- a second spacer 12 made of aluminum nitride AIN or tungsten W.
- the metal part 10 is a plate or plate made of an alloy based on titanium, aluminum and vanadium (TA6V).
- the part made of ceramic material 20 may consist of a plate or plate of monolithic (or solid) silicon carbide, or of material "A410" or "A500” as mentioned above.
- the piece of ceramic material 20 is a composite material with a ceramic matrix.
- This ceramic matrix can be single-phase - for example entirely made of SiC - or multiphase, for example additionally containing at least one phase with self-healing property as described in patent FR 2,732,338.
- the CMC material consists of a fibrous carbon reinforcement and a sequenced ceramic matrix, alternating relatively flexible layers capable of deflecting cracks and layers of rigid ceramic material. It is recalled that such a material is here called “A500”. It can be obtained by a production process as described in patent application FR 2,742,433.
- thermo-structural composite materials include: carbon / carbon composites (C / C) and ceramic matrix composites (CMC) such as C / SiC or SiC / SiC (carbon fiber reinforcement or SiC and matrix silicon carbide) or C / C-SiC (carbon fiber reinforcement and mixed carbon matrix and silicon carbide) or C / Si-BC (carbon fiber reinforcement and self-healing matrix) or C / C-SiC -Si (composite C / C silicided by reaction with Si).
- C / C carbon / carbon composites
- CMC ceramic matrix composites
- CMC such as C / SiC or SiC / SiC (carbon fiber reinforcement or SiC and matrix silicon carbide) or C / C-SiC (carbon fiber reinforcement and mixed carbon matrix and silicon carbide) or C / Si-BC (carbon fiber reinforcement and self-healing matrix) or C / C-SiC -Si (composite C / C silicided by reaction with Si).
- the first part 11 has a massive structure. This part 11 is then made of sufficiently ductile material to deform and thus compensate for the difference in expansion between the metallic and ceramic parts.
- the dimensions of this first intermediate piece 11 and, in particular, its thickness, must be sufficient for this part to be able to play its role of deformable part without reaching excessively large deformations.
- the first spacer 11 is made of substantially pure titanium, T40. T30 or T60 could also be used.
- Table 1 below groups together six assemblies in accordance with Figure 1 described above.
- the composition (A410 or A500) of the piece of ceramic material 20, the composition (AIN or W) of the second interlayer 12, the composition (T40, substantially pure titanium) of the first interlayer 11 and the composition are respectively given.
- alloy of titanium, aluminum and vanadium TA6V of the metal part 10.
- This brazing consists either of an Ag-Mn type brazing (Mn 15%), or of an Ag-Cu-Ti type brazing (63 Ag; 35.25 Cu; 1.75 Ti).
- an AgZr solder Zr 3%) could be used.
- these assemblies were subjected to shear tests using a test piece comprising a symmetrized assembly: CMC part / W or AIN insert / Ti insert / titanium-based metal part / Ti insert / W or AIN insert. / CMC piece.
- the end pieces made of CMC materials have been immobilized in lateral jaws, while the metal piece in the center is subjected to a transverse force, which generally exerts shear stresses in the two intermediate zones between each end piece in CMC and the central metal part, at the level of the spacers.
- shear strength of assembly # 1 is equal to 50% of the shear strength of material A500.
- the shear strength of the assembly obtained according to the invention reaches or even exceeds (in the most favorable cases) the shear strength of the part made of CMC material. This constitutes a decisive quality for such mechanical assembly (resistance of the joint reaching a value equal to or greater than the assembled parts).
- FIG. 2 represents another assembly in accordance with the invention, in which the first insert 11 ′ is constituted by a deformable structure ("compiling" in English).
- the intermediate piece 11 ′ can be formed by a deformable sheet 16 comprising concentric undulations and flat areas 14 arranged alternately on the opposite ridges of the undulations, or on only some of these ridges. These flat areas 14 are brazed alternately, according to their orientation, either on the metal part 10 or on the second insert 12.
- this deformable structure 11 ' is constituted by a part whose general shape is that of a ribbon folded in accordion defining curved parts turned alternately towards the metal part 10 and towards the second interlayer 12.
- the assembly of the invention can be implemented in a turbomachine and, more particularly, in a turbojet engine.
- the metal part 10 can belong to a casing of the turbojet engine and said ceramic part can be: a nozzle flap, a part of the combustion chamber or a post-combustion flame catching arm.
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
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Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR0553788A FR2894498B1 (fr) | 2005-12-08 | 2005-12-08 | Assemblage par brasage entre une piece metallique a base de titane et une piece en materiau ceramique a base de carbure de silicium (sic) et/ou de carbone |
PCT/FR2006/051317 WO2007066051A2 (fr) | 2005-12-08 | 2006-12-08 | Assemblage par brasage entre une piece metallique a base de titane et une piece en materiau ceramique a base de carbure de silicium (sic) et/ou de carbone |
Publications (2)
Publication Number | Publication Date |
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EP1966107A2 true EP1966107A2 (de) | 2008-09-10 |
EP1966107B1 EP1966107B1 (de) | 2018-02-07 |
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EP06842128.8A Active EP1966107B1 (de) | 2005-12-08 | 2006-12-08 | Gelötete verbindung zwischen einem metallteil auf titanbasis und einem keramischen teil auf basis von siliciumcarbid (sic) und/oder kohlenstoff |
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US (1) | US8161753B2 (de) |
EP (1) | EP1966107B1 (de) |
JP (1) | JP5200283B2 (de) |
CN (1) | CN101326140B (de) |
CA (1) | CA2632712C (de) |
FR (1) | FR2894498B1 (de) |
RU (1) | RU2416587C2 (de) |
WO (1) | WO2007066051A2 (de) |
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CN102009239A (zh) * | 2010-10-15 | 2011-04-13 | 北京航空航天大学 | 一种用于碳基材料及其制品的连接方法 |
Families Citing this family (17)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR2920327B1 (fr) * | 2007-08-30 | 2009-11-20 | Snecma | Fraise a rainurer pour usinage a grande avance et a faible profondeur de passe |
EP2233835A1 (de) * | 2009-03-23 | 2010-09-29 | Siemens Aktiengesellschaft | Mit Keramikeinsätzen hartgelötete Brennkammer |
EP2492444A1 (de) * | 2011-02-22 | 2012-08-29 | General Electric Company | Metall-Keramik-Fügeverfahren für Gasturbinen durch Metallisierung eines Teils aus Keramik-Matrix-Verbundwerkstoff |
US8997496B2 (en) | 2011-06-29 | 2015-04-07 | United Technologies Corporation | Hybrid exhaust component |
CN102357694A (zh) * | 2011-09-02 | 2012-02-22 | 上海朝日低碳新能源有限公司 | 一种实现碳纤维与金属的焊接方法 |
FR3001452B1 (fr) * | 2013-01-29 | 2015-02-13 | Herakles | Procede de fabrication d'un panneau d'attenuation acoustique de forme courbee |
WO2014164859A2 (en) | 2013-03-11 | 2014-10-09 | Rolls-Royce Corporation | Compliant layer for ceramic components and methods of forming the same |
US9586868B2 (en) * | 2013-08-29 | 2017-03-07 | United Technologies Corporation | Method for joining dissimilar engine components |
US9757802B2 (en) | 2014-06-30 | 2017-09-12 | General Electric Company | Additive manufacturing methods and systems with fiber reinforcement |
US9333578B2 (en) | 2014-06-30 | 2016-05-10 | General Electric Company | Fiber reinforced brazed components and methods |
US9677845B2 (en) | 2015-04-02 | 2017-06-13 | Lancer Systems L.P. | Firearm handguard having heat-reducing features |
US11619387B2 (en) | 2015-07-28 | 2023-04-04 | Rolls-Royce Corporation | Liner for a combustor of a gas turbine engine with metallic corrugated member |
US10365061B1 (en) * | 2016-12-29 | 2019-07-30 | Aaron E. Painter | Firearm barrel with non-metal outer sleeve |
FR3095151B1 (fr) | 2019-04-16 | 2021-05-14 | Commissariat Energie Atomique | Procede d’assemblage d’une piece en carbone et d’une piece metallique par brasage |
FR3095150B1 (fr) | 2019-04-16 | 2021-07-16 | Commissariat Energie Atomique | Procede d’assemblage d’une piece en carbone et d’une piece metallique en deux etapes |
CN111875403A (zh) * | 2020-09-04 | 2020-11-03 | 宁波材料所杭州湾研究院 | 用于连接碳化硅材料的连接材料、系统、连接结构及应用 |
FR3118721B1 (fr) | 2021-01-11 | 2023-05-12 | Commissariat Energie Atomique | Procede de preparation de la surface d’une piece et procede d’assemblage par brasage direct d’une piece ainsi preparee |
Family Cites Families (15)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3998632A (en) * | 1972-04-27 | 1976-12-21 | Valentin Petrovich Kosteruk | Metal alloy |
US3977869A (en) * | 1975-08-14 | 1976-08-31 | Eutectic Corporation | Indium-containing, low silver copper-base filler metal |
US4239502A (en) * | 1978-11-17 | 1980-12-16 | General Electric Company | Diamond and cubic boron nitride grinding wheels with improved silver alloy bonds |
EP0058206B1 (de) * | 1980-09-01 | 1985-10-16 | Mitsubishi Materials Corporation | Auftragsmaterial zum Löten bestehend aus Cu-Ag legierungen |
JPS5797891A (en) * | 1980-12-08 | 1982-06-17 | Mitsubishi Metal Corp | Cu-ag alloy brazing material |
JPS60226464A (ja) | 1984-04-20 | 1985-11-11 | 日本特殊陶業株式会社 | セラミックと金属との接合構造 |
FR2616696B1 (fr) * | 1987-06-17 | 1993-05-07 | Innovatique Sa | Procede de brasage au four sous atmosphere rarefiee ou controlee de deux pieces |
JPH01205053A (ja) * | 1988-02-12 | 1989-08-17 | Ngk Spark Plug Co Ltd | セラミックと金属との接合応力緩衝合金、およびその緩衝合金を用いたセラミックと金属との接合体 |
JP3005637B2 (ja) * | 1990-05-18 | 2000-01-31 | 日本セメント株式会社 | 金属―セラミックス接合体 |
US5402032A (en) | 1992-10-29 | 1995-03-28 | Litton Systems, Inc. | Traveling wave tube with plate for bonding thermally-mismatched elements |
FR2732338B1 (fr) * | 1995-03-28 | 1997-06-13 | Europ Propulsion | Materiau composite protege contre l'oxydation par matrice auto-cicatrisante et son procede de fabrication |
US6131797A (en) * | 1998-11-16 | 2000-10-17 | Alliedsignal Inc. | Method for joining ceramic to metal |
US6655695B1 (en) * | 2001-02-13 | 2003-12-02 | Honeywell International Inc. | Face seal assembly with composite rotor |
FR2855557B1 (fr) * | 2003-05-26 | 2007-03-02 | Snecma Moteurs | Volet de tuyere a duree de vie augmentee pour turbomoteurs d'avion. |
FR2894499B1 (fr) | 2005-12-08 | 2011-04-01 | Snecma | Assemblage entre une piece metallique et une piece en materiau ceramique a base de sic et/ou de c |
-
2005
- 2005-12-08 FR FR0553788A patent/FR2894498B1/fr active Active
-
2006
- 2006-12-08 EP EP06842128.8A patent/EP1966107B1/de active Active
- 2006-12-08 RU RU2008127504A patent/RU2416587C2/ru active
- 2006-12-08 US US12/096,489 patent/US8161753B2/en active Active
- 2006-12-08 JP JP2008543881A patent/JP5200283B2/ja active Active
- 2006-12-08 WO PCT/FR2006/051317 patent/WO2007066051A2/fr active Application Filing
- 2006-12-08 CA CA2632712A patent/CA2632712C/fr active Active
- 2006-12-08 CN CN2006800463863A patent/CN101326140B/zh active Active
Non-Patent Citations (1)
Title |
---|
See references of WO2007066051A3 * |
Cited By (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CN102009239A (zh) * | 2010-10-15 | 2011-04-13 | 北京航空航天大学 | 一种用于碳基材料及其制品的连接方法 |
CN102009239B (zh) * | 2010-10-15 | 2012-09-05 | 北京航空航天大学 | 一种用于碳基材料及其制品的连接方法 |
Also Published As
Publication number | Publication date |
---|---|
RU2416587C2 (ru) | 2011-04-20 |
WO2007066051A2 (fr) | 2007-06-14 |
JP5200283B2 (ja) | 2013-06-05 |
WO2007066051A3 (fr) | 2007-08-02 |
CA2632712C (fr) | 2013-09-10 |
US20090068004A1 (en) | 2009-03-12 |
RU2008127504A (ru) | 2010-01-20 |
CN101326140B (zh) | 2012-07-04 |
JP2009519880A (ja) | 2009-05-21 |
CN101326140A (zh) | 2008-12-17 |
US8161753B2 (en) | 2012-04-24 |
FR2894498B1 (fr) | 2009-07-10 |
FR2894498A1 (fr) | 2007-06-15 |
CA2632712A1 (fr) | 2007-06-14 |
EP1966107B1 (de) | 2018-02-07 |
WO2007066051B1 (fr) | 2007-09-13 |
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